Add to ORKGDetailed studies of the boundary layer profile and the characteristics of the flow velocity distribution close to the leading edge of a helicopter blade profile were conducted using the embedded laser doppler velocimetry (ELDV) and stereo-PIV. The relatively small scales of flow structures related to dynamic stall, motivated an additional 2C-PIV study in which the flow field has been measured with a relatively high spatial resolution. The feasibility of PIV measurements utilizing a mirror telescope in a wind tunnel has been demonstrated successfully. The spatial resolution of approximately 50 μm allowed a judgment on the choice of turbulence models and damping coefficients for the improvement of CFD predictions
The helicopter group at the DLR in Göttingen has been actively involved in the development of measur...
Validation and improvement of numerical results obtained nowadays on helicopter rotor blade aerodyna...
This work examined the wake aerodynamics of a single helicopter rotor blade with several tip shapes ...
Studies of the boundary layer profile and of the characteristics of the flow velocity distribution c...
The advancement of flow measurement techniques continues to extend experimental boundaries and thus ...
With increasing use of civil helicopters the problem of noise emission of helicopters become more an...
Dynamic stall has proven to be a complex problem in helicopter aerodynamics because it limits the he...
The stereo PIV measurement were performed behind a wing in the plane perpendicular to the flow to st...
Particle image velocimetry (PIV) experiments have been performed in order to derive quantitative flo...
The advancement of measurement systems and technology keeps pushing experimental aerodynamics, which...
The present paper describes an experiment performed in a transonic wind tunnel facility where a new ...
The physical structure and the evolution of helicopter blade tip vortices, particularly the effect o...
The flow field around a helicopter is characterised by its inherent complexity including effects of...
Information on unsteady separation and dynamic stall is being obtained from two experimental program...
Particle image velocimetry (PIV) is increasingly used to investigate unsteady velocity fields instan...
The helicopter group at the DLR in Göttingen has been actively involved in the development of measur...
Validation and improvement of numerical results obtained nowadays on helicopter rotor blade aerodyna...
This work examined the wake aerodynamics of a single helicopter rotor blade with several tip shapes ...
Studies of the boundary layer profile and of the characteristics of the flow velocity distribution c...
The advancement of flow measurement techniques continues to extend experimental boundaries and thus ...
With increasing use of civil helicopters the problem of noise emission of helicopters become more an...
Dynamic stall has proven to be a complex problem in helicopter aerodynamics because it limits the he...
The stereo PIV measurement were performed behind a wing in the plane perpendicular to the flow to st...
Particle image velocimetry (PIV) experiments have been performed in order to derive quantitative flo...
The advancement of measurement systems and technology keeps pushing experimental aerodynamics, which...
The present paper describes an experiment performed in a transonic wind tunnel facility where a new ...
The physical structure and the evolution of helicopter blade tip vortices, particularly the effect o...
The flow field around a helicopter is characterised by its inherent complexity including effects of...
Information on unsteady separation and dynamic stall is being obtained from two experimental program...
Particle image velocimetry (PIV) is increasingly used to investigate unsteady velocity fields instan...
The helicopter group at the DLR in Göttingen has been actively involved in the development of measur...
Validation and improvement of numerical results obtained nowadays on helicopter rotor blade aerodyna...
This work examined the wake aerodynamics of a single helicopter rotor blade with several tip shapes ...